Transition Measurement on Metallic Aircraft Model in Typical Lowspeed Wind Tunnel

The work described here relates to the method measuring the boundary layer transition at “lowspeed” and “atmospheric” wind tunnel for an aircraft model made by metal. The objective of the research is to improve the test technique and to know a precise procedure about transition measurements, especially for an aircraft model at such type of typical wind tunnel. At JAXA 6.5m×5.5m Lowspeed Wind Tunnel (LWT1), the boundary layer growing on the left-wing of the ONERA-Model was investigated using two kinds of the visualizing methods, namely Temperature-Sensitive Liquid Crystal Film and Infrared Ray (IR) Camera. Throughout the experiment, a lot of knowledge was obtained. Comparison of the results from two devices showed that IR camera has possibility to be more effective using after cooling of model surface.